FR2992353A1 - ASSEMBLY OF AN EXHAUST CONE AND EXHAUST CASE IN A GAS TURBINE ENGINE - Google Patents
ASSEMBLY OF AN EXHAUST CONE AND EXHAUST CASE IN A GAS TURBINE ENGINE Download PDFInfo
- Publication number
- FR2992353A1 FR2992353A1 FR1255853A FR1255853A FR2992353A1 FR 2992353 A1 FR2992353 A1 FR 2992353A1 FR 1255853 A FR1255853 A FR 1255853A FR 1255853 A FR1255853 A FR 1255853A FR 2992353 A1 FR2992353 A1 FR 2992353A1
- Authority
- FR
- France
- Prior art keywords
- flange
- exhaust
- cone
- orifices
- flanges
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 1
- 238000011144 upstream manufacturing Methods 0.000 claims description 16
- 210000003462 vein Anatomy 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 5
- 238000002485 combustion reaction Methods 0.000 claims description 2
- 241000842962 Apoda limacodes Species 0.000 claims 4
- 238000004519 manufacturing process Methods 0.000 claims 3
- 239000000463 material Substances 0.000 claims 2
- 230000000717 retained effect Effects 0.000 claims 2
- 238000010586 diagram Methods 0.000 claims 1
- 238000007599 discharging Methods 0.000 claims 1
- 230000002349 favourable effect Effects 0.000 claims 1
- 238000003780 insertion Methods 0.000 claims 1
- 230000037431 insertion Effects 0.000 claims 1
- 239000003921 oil Substances 0.000 claims 1
- 238000010079 rubber tapping Methods 0.000 claims 1
- 238000007789 sealing Methods 0.000 claims 1
- 229910000679 solder Inorganic materials 0.000 claims 1
- 230000000930 thermomechanical effect Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/04—Mounting of an exhaust cone in the jet pipe
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/90—Mounting on supporting structures or systems
- F05D2240/91—Mounting on supporting structures or systems on a stationary structure
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
La présente invention porte sur un ensemble formé, dans un moteur à turbine à gaz, d'un carter d'échappement (17) et d'un cône d'échappement (19), le carter d'échappement et le cône d'échappement étant fixés par des moyens mécaniques de fixation l'un à l'autre. L'ensemble est caractérisé par le fait que le carter d'échappement et le cône d'échappement comprennent chacun une bride annulaire axiale, les deux brides étant engagées l'une dans l'autre, l'une étant extérieure l'autre intérieure, et maintenues assemblées par les moyens mécaniques.The present invention relates to an assembly formed, in a gas turbine engine, of an exhaust casing (17) and an exhaust cone (19), the exhaust casing and the exhaust cone being fixed by mechanical fixing means to one another. The assembly is characterized in that the exhaust casing and the exhaust cone each comprise an axial annular flange, the two flanges being engaged one inside the other, one being external the other inner, and held together by mechanical means.
Description
Domaine technique La présente invention porte sur un turboréacteur et vise le montage du cône d'échappement situé à l'arrière du moteur sur le carter d'échappement de celui-ci. Etat de la technique Un turboréacteur comprend une manche d'entrée d'air, à l'amont, par laquelle l'air est aspiré dans le moteur et une tuyère à l'aval par laquelle les gaz chauds produits par la combustion d'un carburant sont éjectés pour fournir une partie de la poussée au moins. Entre la manche d'entrée et la tuyère d'éjection des gaz, l'air aspiré est comprimé par des moyens de compression, chauffé et détendu dans des turbines qui entraînent les moyens de compression. Les turboréacteurs multi-flux comportent en plus, au moins un rotor de soufflante déplaçant une masse importante d'air, formant le flux secondaire et fournissant l'essentiel de la poussée, le flux primaire étant la partie du flux d'air aspiré qui est chauffée puis détendue dans la turbine, avant d'être éjectée à travers la tuyère de flux primaire.TECHNICAL FIELD The present invention relates to a turbojet and aims at mounting the exhaust cone located at the rear of the engine on the exhaust casing thereof. STATE OF THE ART A turbojet comprises an upstream air inlet sleeve through which air is drawn into the engine and a downstream nozzle through which the hot gases produced by the combustion of a fuel are ejected to provide a portion of the thrust at least. Between the inlet sleeve and the gas ejection nozzle, the sucked air is compressed by compression means, heated and expanded in turbines which drive the compression means. The multi-flow turbojets additionally comprise at least one blower rotor displacing a large mass of air, forming the secondary flow and providing the bulk of the thrust, the primary flow being the part of the intake air flow which is heated then relaxed in the turbine, before being ejected through the primary flow nozzle.
Un turboréacteur est constitué de rotors montés sur une structure fixe par l'intermédiaire de paliers. La structure fixe présente à l'amont un carter supportant les paliers amont et formant le carter dit intermédiaire. A l'aval du moteur, la structure supportant les paliers forme le carter d'échappement. Ce dernier comprend un moyeu et des viroles annulaires reliées entre elles par des bras radiaux, ces derniers traversant la veine de flux primaire.A turbojet consists of rotors mounted on a fixed structure by means of bearings. The fixed structure has upstream a housing supporting the upstream bearings and forming the so-called intermediate housing. Downstream of the engine, the structure supporting the bearings forms the exhaust casing. The latter comprises a hub and annular ferrules interconnected by radial arms, the latter crossing the primary flow vein.
En aval du carter d'échappement la veine est délimitée extérieurement par la tuyère d'éjection du flux primaire et, intérieurement, par une pièce de forme globalement tronconique que l'on désigne par l'expression cône d'échappement. Cette pièce est généralement fixée par boulonnage au carter d'échappement. La présente invention vise le mode de fixation du cône d'échappement au carter d'échappement. Des turboréacteurs de l'art antérieur, tels que ceux de la famille de moteurs CFM 56 de la demanderesse, sont pourvus d'un cône d'échappement monté sur le carter d'échappement.Downstream of the exhaust casing, the vein is delimited externally by the ejection nozzle of the primary flow and, internally, by a generally frustoconical shaped part that is designated by the expression exhaust cone. This part is usually bolted to the exhaust housing. The present invention relates to the method of fixing the exhaust cone to the exhaust casing. Prior art turbojet engines, such as those of the CFM 56 family of engines of the applicant, are provided with an exhaust cone mounted on the exhaust casing.
Selon un mode de fixation connu, le carter d'échappement est pourvu d'une bride annulaire, orientée radialement dans un plan transversal, reliée par des boulons à une bride correspondante sur le bord amont du cône d'échappement. Les boulons ont ainsi une orientation axiale et sont logés dans des poches ménagées dans la paroi de cône d'échappement, pour en permettre l'accès depuis la veine de gaz. Au montage du cône sur le carter les pièces sont positionnées bride contre bride, des moyens mécaniques de fixation tels que des boulons ou des vis sont glissés dans les poches de manière à ce qu'ils soient engagés dans les orifices des brides et vissés. Il est nécessaire, après mise en place des moyens de fixation de recouvrir chacune des poches d'un capot de fermeture pour assurer la continuité de la veine de gaz et limiter l'impact aérodynamique. Par exemple, il faut ménager douze poches avec capots de fermeture pour la fixation d'un cône d'échappement sur un moteur CFM. Il existe un besoin pour une solution plus simple à mettre en oeuvre nécessitant moins de pièces à gérer. Ce mode d'assemblage induit aussi une masse propre qu'il est aussi souhaitable de réduire.According to a known method of attachment, the exhaust casing is provided with an annular flange, oriented radially in a transverse plane, connected by bolts to a corresponding flange on the upstream edge of the exhaust cone. The bolts have an axial orientation and are housed in pockets in the exhaust cone wall, to allow access from the gas stream. When mounting the cone on the housing the parts are positioned flange against flange, mechanical fixing means such as bolts or screws are slid into the pockets so that they are engaged in the orifices of the flanges and screwed. It is necessary, after installation of the fastening means to cover each of the pockets of a closure cap to ensure the continuity of the gas stream and limit the aerodynamic impact. For example, it is necessary to spare twelve pockets with closing caps for fixing an exhaust cone on a CFM engine. There is a need for a simpler solution to implement requiring fewer parts to manage. This method of assembly also induces a clean mass which it is also desirable to reduce.
Selon un autre mode de fixation connu, le cône d'échappement est en deux parties : une partie amont et une partie aval. La partie amont du cône est montée sur le carter d'échappement de la même façon que précédemment par boulonnage de deux brides radiales avec des boulons orientés axialement. On évite cependant l'aménagement de poches sur la partie amont du cône car on peut avoir accès à la zone de liaison du cône avec le carter d'échappement par l'intérieur de la partie amont du cône, après avoir enlevé la partie arrière. Au montage, on met en place d'abord la partie amont du cône contre la bride du carter, on introduit les boulons par l'ouverture aval de cette partie et on solidarise les brides l'une à l'autre. L'espace est suffisant pour effectuer ces opérations depuis l'arrière. Une fois la fixation terminée, la partie aval du cône d'échappement est mise en place sur la partie amont et fixée également par boulonnage mais ici les surfaces de liaison sont orientées tangentiellement aux parois du cône. On note que cette solution rend les opérations de démontage / montage plus lourdes. Elle nécessite l'emploi d'un nombre de boulons double de la solution précédente et l'aménagement d'une bride supplémentaire. Cette masse en porte à faux n'est pas souhaitable sur le plan du comportement dynamique de la partie arrière du moteur.According to another known method of attachment, the exhaust cone is in two parts: an upstream part and a downstream part. The upstream portion of the cone is mounted on the exhaust casing in the same manner as previously by bolting two radial flanges with axially oriented bolts. However, it avoids the development of pockets on the upstream part of the cone because one can have access to the cone connecting zone with the exhaust casing through the inside of the upstream portion of the cone, after removing the rear portion. During assembly, the upstream part of the cone is first placed against the flange of the casing, the bolts are introduced through the downstream opening of this part and the flanges are secured to one another. There is enough space to perform these operations from behind. Once the fixing is completed, the downstream part of the exhaust cone is placed on the upstream part and also fixed by bolting but here the connecting surfaces are oriented tangentially to the walls of the cone. Note that this solution makes disassembly / mounting operations heavier. It requires the use of a number of double bolts of the previous solution and the installation of an additional flange. This cantilevered mass is undesirable in terms of the dynamic behavior of the rear part of the engine.
Claims (8)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1255853A FR2992353B1 (en) | 2012-06-21 | 2012-06-21 | ASSEMBLY OF AN EXHAUST CONE AND EXHAUST CASE IN A GAS TURBINE ENGINE |
US14/403,305 US9897011B2 (en) | 2012-06-21 | 2013-06-20 | Gas turbine engine comprising an exhaust cone attached to the exhaust casing |
GB1421714.5A GB2516604B (en) | 2012-06-21 | 2013-06-20 | Gas turbine engine comprising an exhaust cone attached to the exhaust casing |
PCT/FR2013/051450 WO2013190246A1 (en) | 2012-06-21 | 2013-06-20 | Gas turbine engine comprising an exhaust cone attached to the exhaust casing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1255853A FR2992353B1 (en) | 2012-06-21 | 2012-06-21 | ASSEMBLY OF AN EXHAUST CONE AND EXHAUST CASE IN A GAS TURBINE ENGINE |
Publications (2)
Publication Number | Publication Date |
---|---|
FR2992353A1 true FR2992353A1 (en) | 2013-12-27 |
FR2992353B1 FR2992353B1 (en) | 2016-12-30 |
Family
ID=47022774
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1255853A Active FR2992353B1 (en) | 2012-06-21 | 2012-06-21 | ASSEMBLY OF AN EXHAUST CONE AND EXHAUST CASE IN A GAS TURBINE ENGINE |
Country Status (4)
Country | Link |
---|---|
US (1) | US9897011B2 (en) |
FR (1) | FR2992353B1 (en) |
GB (1) | GB2516604B (en) |
WO (1) | WO2013190246A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016128642A1 (en) | 2015-02-09 | 2016-08-18 | Peugeot Citroen Automobiles Sa | Turbocharged engine assembly having two exhaust ducts comprising a recirculation line |
US9551239B2 (en) * | 2015-04-22 | 2017-01-24 | Rohr, Inc. | Exhaust assembly center body |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2994712B1 (en) * | 2012-08-27 | 2018-04-13 | Safran Aircraft Engines | METHOD FOR ASSEMBLING A TUBE AND AN EXHAUST HOUSING OF A TURBOMACHINE |
US9732701B2 (en) | 2014-05-12 | 2017-08-15 | Rohr, Inc. | Center body attachment system |
US9784215B2 (en) * | 2014-11-07 | 2017-10-10 | Rohr, Inc. | Exhaust nozzle center body attachment |
US10451001B2 (en) * | 2014-12-09 | 2019-10-22 | Rolls-Royce Corporation | CMC oxide-oxide mixer design |
US10907508B2 (en) * | 2015-11-12 | 2021-02-02 | Rohr, Inc. | Turbine engine and exhaust system connection |
FR3051831B1 (en) * | 2016-05-26 | 2018-05-18 | Safran Aircraft Engines | TURBOMACHINE EXHAUST CASE AND METHOD FOR MANUFACTURING THE SAME |
KR20220091173A (en) | 2020-12-23 | 2022-06-30 | 한화에어로스페이스 주식회사 | Tail cone and assembling method of tail cone |
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---|---|---|---|---|
US2945704A (en) * | 1957-07-23 | 1960-07-19 | Hughes Aircraft Co | Nose section-quick disconnect |
JP2000018096A (en) * | 1998-07-02 | 2000-01-18 | Ishikawajima Harima Heavy Ind Co Ltd | Jet engine tail cone supporting device |
EP0979974A2 (en) * | 1998-08-11 | 2000-02-16 | Allison Advanced Development Company | Method and apparatus for spraying fuel within a gas turbine engine |
DE10036211A1 (en) * | 2000-07-25 | 2002-02-07 | Rolls Royce Deutschland | Combustion chamber shingle for aviation gas turbine has plate-form base component with hole for threaded bolt with head fixed in recess by clamping connection formed by deformation of edge section of head recess or bolt head |
US20080060344A1 (en) * | 2006-09-11 | 2008-03-13 | Pratt & Whitney Canada Corp. | Exhaust duct and tail cone attachment of aircraft engines |
EP2161431A2 (en) * | 2008-09-03 | 2010-03-10 | Rolls-Royce Deutschland Ltd & Co KG | Inlet nose cone for an aircraft gas turbine powerplant |
EP2202388A1 (en) * | 2008-12-23 | 2010-06-30 | Techspace Aero S.A. | Flange architecture |
US20110036068A1 (en) * | 2009-08-17 | 2011-02-17 | Guy Lefebvre | Gas turbine engine exhaust mixer |
FR2955152A1 (en) * | 2010-01-11 | 2011-07-15 | Snecma | Turbomachine i.e. open rotor type jet engine, for aircraft, has evacuation unit including envelope connected to structural annular walls and extended around enclosure to determine outer and inner annular cavities in space |
FR2961788A1 (en) * | 2010-06-29 | 2011-12-30 | Aircelle Sa | TURBOREACTOR NACELLE |
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FR2623249A1 (en) * | 1987-11-12 | 1989-05-19 | Snecma | ASSEMBLY CONSISTING OF TWO PIECES OF MATERIALS HAVING DIFFERENT EXPANSION COEFFICIENTS, CONNECTED THEREBY AND METHOD OF ASSEMBLY |
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US7384075B2 (en) * | 2004-05-14 | 2008-06-10 | Allison Advanced Development Company | Threaded joint for gas turbine components |
ES2311917T3 (en) | 2005-11-08 | 2009-02-16 | Siemens Aktiengesellschaft | PROVISION FOR CLAMPING A TUBE ON A PERIPHERAL SURFACE. |
FR2978988B1 (en) | 2011-08-12 | 2013-07-26 | Aircelle Sa | EJECTION CONE FOR AIRCRAFT TURBOJET ENGINE |
FR2994712B1 (en) | 2012-08-27 | 2018-04-13 | Safran Aircraft Engines | METHOD FOR ASSEMBLING A TUBE AND AN EXHAUST HOUSING OF A TURBOMACHINE |
-
2012
- 2012-06-21 FR FR1255853A patent/FR2992353B1/en active Active
-
2013
- 2013-06-20 GB GB1421714.5A patent/GB2516604B/en active Active
- 2013-06-20 WO PCT/FR2013/051450 patent/WO2013190246A1/en active Application Filing
- 2013-06-20 US US14/403,305 patent/US9897011B2/en active Active
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
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US2945704A (en) * | 1957-07-23 | 1960-07-19 | Hughes Aircraft Co | Nose section-quick disconnect |
JP2000018096A (en) * | 1998-07-02 | 2000-01-18 | Ishikawajima Harima Heavy Ind Co Ltd | Jet engine tail cone supporting device |
EP0979974A2 (en) * | 1998-08-11 | 2000-02-16 | Allison Advanced Development Company | Method and apparatus for spraying fuel within a gas turbine engine |
DE10036211A1 (en) * | 2000-07-25 | 2002-02-07 | Rolls Royce Deutschland | Combustion chamber shingle for aviation gas turbine has plate-form base component with hole for threaded bolt with head fixed in recess by clamping connection formed by deformation of edge section of head recess or bolt head |
US20080060344A1 (en) * | 2006-09-11 | 2008-03-13 | Pratt & Whitney Canada Corp. | Exhaust duct and tail cone attachment of aircraft engines |
EP2161431A2 (en) * | 2008-09-03 | 2010-03-10 | Rolls-Royce Deutschland Ltd & Co KG | Inlet nose cone for an aircraft gas turbine powerplant |
EP2202388A1 (en) * | 2008-12-23 | 2010-06-30 | Techspace Aero S.A. | Flange architecture |
US20110036068A1 (en) * | 2009-08-17 | 2011-02-17 | Guy Lefebvre | Gas turbine engine exhaust mixer |
FR2955152A1 (en) * | 2010-01-11 | 2011-07-15 | Snecma | Turbomachine i.e. open rotor type jet engine, for aircraft, has evacuation unit including envelope connected to structural annular walls and extended around enclosure to determine outer and inner annular cavities in space |
FR2961788A1 (en) * | 2010-06-29 | 2011-12-30 | Aircelle Sa | TURBOREACTOR NACELLE |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016128642A1 (en) | 2015-02-09 | 2016-08-18 | Peugeot Citroen Automobiles Sa | Turbocharged engine assembly having two exhaust ducts comprising a recirculation line |
US9551239B2 (en) * | 2015-04-22 | 2017-01-24 | Rohr, Inc. | Exhaust assembly center body |
Also Published As
Publication number | Publication date |
---|---|
FR2992353B1 (en) | 2016-12-30 |
GB201421714D0 (en) | 2015-01-21 |
US9897011B2 (en) | 2018-02-20 |
GB2516604A (en) | 2015-01-28 |
US20150152788A1 (en) | 2015-06-04 |
WO2013190246A1 (en) | 2013-12-27 |
GB2516604B (en) | 2020-04-22 |
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